ANGLED HEAT TRANSFER PEDESTAL
A gas turbine engine component includes a body defining a cooling inlet and a cooling outlet in fluid communication through a cooling channel extending through the body, and a plurality of pedestals positioned in the cooling channel. The plurality of pedestals arranged such that the adjacent pedestals alternatingly converge toward a first wall of the cooling channel and toward a second wall, opposite the first wall. A gas turbine engine includes a combustor, and a plurality of gas turbine engine components positioned in fluid communication with the combustor. Each component includes a body defining a cooling inlet and a cooling outlet in fluid communication through a cooling channel extending through the body. A plurality of pedestals are positioned in the cooling channel and are arranged such that the adjacent pedestals alternatingly converge toward a first wall of the cooling channel and toward a second wall, opposite the first wall.
1 . A gas turbine engine component, comprising:
a body defining a cooling inlet and a cooling outlet in fluid communication with each other through a cooling channel extending through the body; and
a plurality of pedestals disposed in the cooling channel, the plurality of pedestals arranged such that the adjacent pedestals alternatingly converge toward a first wall of the cooling channel and toward a second wall of the cooling channel, opposite the first wall.
2 . The gas turbine engine component of claim 1 , further comprising a plurality of pedestals arranged in a plurality of longitudinally-extending rows.
3 . The gas turbine engine component of claim 1 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a component longitudinal axis.
4 . The gas turbine engine component of claim 1 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a radial axis of the component.
5 . The gas turbine engine component of claim 1 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a radial axis of the component and at an angle between 10 degrees and 90 degrees relative to a longitudinal axis of the component.
6 . The gas turbine engine component of claim 1 , wherein the arrangement of the plurality of pedestals is selected to reduce stresses at the component and/or to improve thermal energy transfer between the component and a cooling airflow directed therethrough.
7 . The gas turbine engine component of claim 1 , wherein the arrangement of the plurality of pedestals defines a truss-like structure.
8 . An airfoil for a gas turbine engine, comprising:
a platform portion;
an airfoil portion extending radially outwardly from the platform portion, the airfoil portion having at least one cooling channel disposed therein; and
a plurality of pedestals disposed in the cooling channel, the plurality of pedestals arranged such that the adjacent pedestals altematingly converge toward a first wall of the cooling channel and toward a second wall of the cooling channel, opposite the first wall.
9 . The airfoil of claim 8 , further comprising a cooling airflow inlet disposed at the platform portion in fluid communication with the cooling channel.
10 . The airfoil of claim 9 , further comprising a cooling airflow outlet disposed at one or more of the airfoil portion or the platform portion in fluid communication with both the cooling channel and the cooling airflow inlet.
11 . The airfoil of claim 10 , wherein the cooling airflow outlet is disposed at one or more of a trailing edge, pressure side or suction side of the airfoil portion, or the platform portion.
12 . The airfoil of claim 8 , further comprising a plurality of pedestals arranged in a plurality of longitudinally-extending rows.
13 . The airfoil of claim 8 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to an airfoil longitudinal axis.
14 . The airfoil of claim 8 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a radial axis of the airfoil.
15 . The airfoil of claim 8 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a radial axis of the airfoil and at an angle between 10 degrees and 90 degrees relative to a longitudinal axis of the airfoil.
16 . The airfoil of claim 8 , wherein the arrangement of the plurality of pedestals is selected to reduce stresses at the airfoil and/or to improve thermal energy transfer between the airfoil and a cooling airflow directed therethrough.
17 . A gas turbine engine, comprising:
a combustor; and
a plurality of gas turbine engine components disposed in fluid communication with the combustor, each gas turbine engine component including:
a body defining a cooling inlet and a cooling outlet in fluid communication with each other through a cooling channel extending through the body; and
a plurality of pedestals disposed in the cooling channel, the plurality of pedestals arranged such that the adjacent pedestals alternatingly converge toward a first wall of the cooling channel and toward a second wall of the cooling channel, opposite the first wall.
18 . The gas turbine engine of claim 17 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a component longitudinal axis.
19 . The gas turbine engine of claim 17 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a radial axis of the component.
20 . The gas turbine engine of claim 17 , wherein at least one pedestal of the plurality of pedestals intersects the first wall and/or the second wall at an angle between 10 degrees and 90 degrees relative to a radial axis of the component and at an angle between 10 degrees and 90 degrees relative to a longitudinal axis of the component.